Airplane.



L. KULCSAR.

AIRPLANE.

APPLICATION FILED Nov. 1. 1917 3 SHEETSSHEET I.

(Jnucufoz Lewis Kudlosa r Patented July 2, 1918.

' 1.. KULCSAR.

AIRPLME.

APPLICATION FILED NOV. 7, 1917- I 1,271,480. Patented July 2,1918.

3 SHEETS'SHEET 2.

Elwue v1 toz Lewis KLLLC cw q vibvuzooao 3 fi gg, 35

L. KULCSAR.

AIRPLANE.

' APPLICATION FILED NOV= 7, I917.

Patented July 2, 1918,

3 SHEETSSHEET\ 3.

iIll v. gwmmto c Lewis KU/[OSOJ LEWIS KULCSAR, OF PUNXSUTAWNEY, PENNSYLVANIA.

AIRPLANE.

Specification of Letters Patent.

Patented July 2,1918."

Application filed November 7, 1917. Serial no. 200,789.

To all whom it may concern:

Be it known that I, Lnwrs KULcsAR, a citizen of the United States, residing at Punxsutawney, in the county of Jefferson and State of Pennsylvania, have invented new and useful Improvements in Airplanes, of which the following is a specification.

This invention relates to airplanes, the object in view being to produce a novel form of airplane which will closely resemble a butterfly and which will be nearly or quite invisible at a comparatively low altitude thus particularly adapting the same for military and naval purposes.

A further object of the invention is to simplify and improve the means for mamtaining the longitudinal and lateral stability of the machine While retaining the ordinary stabilizing means such as the vertical and horizontal rudders, additional stabilizing means, hereinafter referred to as trailing wings, being also useful for emergency purposes, when, for any reason the vertical rudder or horizontal rudder should both become inoperative.

With the above and other objects in view, the inventionconsists in the novel construction,.co1nbination and arrangement of parts, herein described, illustrated and claimed.

In the accompanying drawings Figure 1 is a plan view of the improved airplane.

Fig. 2 is aside elevation thereof.

Fig. 3 is a front elevation of the" same.

Fig. 4c is a cross section through the body or fuselage.

' Fig.5 is a cross section through one of the leading wings. i

Fig. 6 is a cross section through one of the trailing wings.

Referring to the drawings A designates the body or fuselage of the airplane, B the leading wings, C the trailing wings, D the vertical rudder,'I-I the horizontal rudder, I the engine, located at the front end of the fuselage, and K a tractor propeller fast on the engine shaft.

In carrying out the invention, the fuselage A is composed .of longitudinal and transverse frame members 1 and 2 respectively, said members being fpreferably composed of light metal strips 0 angle iron and T-iron construction in cross section. In the substantially rectangular spaces between the frame members 1 and 2, blocks or sheets 3 of mica or other suitable material are permanently fastened in any suitable way.

Each of the leading wings B is likewise composed of a skeleton frame Work or frame members 4 and 5 extending longitudinally and transversely thereof, certain of said frame membersjbeing of angle iron formation and others of T-iron formation and having blocks or sheets 6 of mica or other translucent or semitranslucent material placed within the spaces formed thereby and secured by any suitable means.

In like manner the trailing wings C are formed of frame members 7 and 8 of a formation similar to those above described, the spaces formed by the frame members 7 and 8 being filled with blocks or sheets 9 of mica or like material.

The leading wings B progressively in-- crease in width or chord from the body toward the outer ends thereof, the trailing edges 10 of the leading wings B having a rearward rake and gradually diverging from the leading edges 10 thereof as clearly shown in the plan view Fig. 1. The leading edges 12 of the trailing wings C are substantially parallel to the trailing edges 10 of the leading wings B but arranged in a lower plane so as not to be affected by or to affect the turbulent air leaving the trailing edges of the leading wings. The trailing wings are triangular in shape, having rearwardly diverging inner edges 13 and rearwardly converging outer edges14. This gives to the machine as a whole a close resemblance to a butterfly. The leading edges 12 of the trailing wings C are connected to rock shafts 15 which extend the full length thereof and project at their rear ends into the body or fuselage A where they are provided with operating arms or levers 16 by means of which the aviator is adapted to vary the angle of incidence of the trailing wings. The vertical and horizontal rudders D and H are constructed in the same manner as the leading and trailing wings, of a skeleton frame work and blocks or sheets of mica, in fact this feature of construction is carried out throughout the whole machine so as to render the same invisible or substantiaillly so at a comparatively low altitude. The landing gear comprises a pair of floats or pontoons 17 having planingsurfaces 18 and equipped with froni' and rear wheels or rollers 19 and 20 thusadapting the machine to 1 land upon or rise in flight from either the land or Water. Suitable stay wires 21 connect the leading wings B with the body or fuselage and guy wires 22 serve to brace the rock shafts 15 in relation to the body or fuselage.

From the foregoing description taken in connection with the accompanying drawings it will be understood that by simultaneously elevating the trailing portions of the trailing wings, the air plane will be directed upwardly and conversely by depressing the trailing portions of the trailing wings, the machine will be directed downwardly. By raising one of the trailing Wings and de-. pressing the other trailing wing, any'desired bank may be imparted to the machine. Should the horizontal rudder or the vertical rudder or both become disabled for any reason, by means of the trailing wings C, the machine may be caused to ascend or descend or to turn to the right or to the left by the proper manipulation of the trailing means for said trailing wings. This imparts to the machine a very great factor of safety.

I claim 1. In airplane construction, a fuselage, wings, and trailing surfaces, each of said parts embodying a skeleton frame work consisting of longitudinal and transverse frame members certain of which are of T-formation in cross section and other of which are of angle iron formation in cross section, and sections of substantially transparent material filling the spaces bounded by said frame members between the points of intersection thereof.

In airplane construction. a frame comprising a marginal frame member of angle iron formation, longitudinal and transverse frame members of Tformation, and sections of substantially transparent material filling the spaces bounded by said frame members between the points of intersection thereof.

In testimony whereof I afiix my signature.

LEWIS KULCSAR. 

